星载GPS低轨卫星非差简化动力法精密定轨

发布时间：2018-03-08 02:06

本文选题：GRACE　切入点：精密定轨　出处：《中国地震局地震研究所》2013年硕士论文　论文类型：学位论文

【摘要】：低轨卫星为地球科学带来了革命性的发展阶段，而精密的卫星轨道则是卫星应用于其他科学研究的基础。当前低轨卫星的广泛应用，为低轨卫星精密定轨技术的发展提供了良好的外部环境。非差简化动力学法作为低轨卫星精密定轨的方法之一，充分利用卫星的几何和动力信息，在动力学模型和GPS观测值几何信息之间进行选权平衡，削弱动力学模型误差影响，定轨结果稳定，精度高。固研究低轨卫星的非差简化动力学精密定轨具有一定的意义。论文第一部分首先阐述了卫星导航系统的发展及其目前国内外星载GPS低轨卫星精密定轨的研究现状，，随后介绍了卫星精密定轨的基础理论，包括时间系统、坐标系统以及不同系统之间的转换。阐述了卫星无摄运动的二体问题，描述卫星受摄运动，分析各种摄动力对卫星轨道的影响量级及计算模型。同时介绍了低轨卫星的几何观测模型，主要的误差源及改正方法。论文第二部分详细介绍了简化动力学法定轨的基本原理。以Bernese5.0软件为平台，设计了一套GRACE卫星精密定轨流程，采用2011年年积日213~243共31天的GRACE卫星星载GPS观测数据，通过非差简化动力学法解算GRACE_A卫星与GRACE_B卫星31天的简化动力学轨道，并将结果与JPL发布的事后科学轨道进行比较。结果显示，GRACE_A卫星在切向、法向和径向上的中误差分别为1.29cm、0.87cm和1.52cm；GRACE_B卫星在切向、法向和径向上的中误差分别为1.32cm、0.94cm和1.61cm。两者的3D-RMS值分别为2.17和2.28cm，精度都达到了厘米级。论文最后部分简要介绍了卫星激光测距（SLR）的原理，采用2011年年积日213~243共31天SLR观测数据，检核GRACE_A卫星与GRACE_B卫星的轨道。结果显示，每天反算的站心距与SLR解算的站心距差值中误差均小于5cm，其中31天的平均中误差分别2.5cm与2.6cm。
[Abstract]:Leo satellites have brought a revolutionary stage of development for Earth science, and precise satellite orbits are the basis for satellite applications in other scientific research. It provides a good external environment for the development of precision orbit determination technology for Leo satellites. As one of the methods of precise orbit determination for Leo satellites, the non-differential simplified dynamics method makes full use of the geometric and dynamic information of the satellites. The weight selection balance between the dynamic model and the geometric information of the GPS observation value is carried out, which weakens the influence of the dynamic model error, the orbit determination result is stable and the precision is high. In the first part of the thesis, the development of satellite navigation system and the current research status of satellite GPS Leo satellite precision orbit determination at home and abroad are described, and then the basic theory of satellite precision orbit determination, including time system, is introduced. The transformation of coordinate system and different systems. The two-body problem of satellite's nonperturbed motion is discussed, and the satellite's passive motion is described. The order of magnitude and calculation model of the influence of various perturbation forces on satellite orbit are analyzed. At the same time, the geometric observation model, main error source and correction method of Leo satellite are introduced. In the second part of the paper, the basic principle of simplified dynamical orbit is introduced in detail. A set of precise orbit determination process of GRACE satellite is designed on the platform of Bernese5.0 software. The spaceborne GPS observation data of GRACE satellite are used for 31 days. The simplified dynamic orbit of GRACE_A satellite and GRACE_B satellite for 31 days is calculated by using the non-differential simplified dynamics method, and the results are compared with the post-scientific orbit released by JPL. The results show that the GRACEA satellite is tangentially. The median errors in normal and radial directions are 1.29 cm / m 0.87 cm and 1.52 cm / g GRACEB respectively in tangential direction, 1.32 cm / 0 94 cm and 1.61 cm / m in radial direction, respectively. The 3D-RMS values of both are 2.17 and 2.28 cm respectively, and the accuracy reaches the centimeter level. In the last part of the paper, the principle of satellite laser rangefinder (SLR) is briefly introduced. The 31 days SLR observation data are used to check the orbit of GRACE_A satellite and GRACE_B satellite. The median error of the difference between SLR and SLR is less than 5 cm, and the average error of 31 days is 2.5 cm and 2.6 cm, respectively.
【学位授予单位】：中国地震局地震研究所
【学位级别】：硕士
【学位授予年份】：2013
【分类号】：P228.4

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